Sharif Digital Repository

Metabonomics is a quantitative measurement of time dependent metabolic interactions for living systems in response to the pathological or genetic variations. NMR spectroscopy has emerged as a key tool for understanding metabolic processes in living systems. In this project, the study of metabolomics was performed as classification and regression on samples of parkinson’s disease, multiple sclerosis disease, celiac disease and crohn’s disease. In classification part, various methods were applied using optimal parameters.classification methods in Parkinson’s disease, multiple sclerosis disease, celiac disease and crohn’s disease were RF, CART, PLS-DA, RF and RF respectively. Based on the... 

Foundation is the lowest load-bearing part of a structure and a part of underneath soil that is affected by the structure load. In fact, foundation transfers the loads from the superstructure to the substructure, preventing excessive settlement of soil or stresses exceeding soil bearing capacity. Indeed, almost all structures are placed on the ground, therefore the effects of soil and structure on each other, which is known as Soil Structure Interaction (SSI), is considered as a key factor in many important and engineered structures. In contrast to structures on a rigid footing, a flexible foundation may show stiffness degradation along with an increase of damping and natural period of the... 

In this project three models addressed before in the references are reviewed and the stability margins of radome error slope obtained by analytical method. Then a new model who is usefull in practical applications presented. Because of complication of this model the model is simplified and stability margins for radome error slope derived in simplified model. It is also shown that simplified applicative model is similar to model purposed in ref. [6]. Then a PD controller designed to stabilize some of models reviewed in chapter 3. The equations derived before verified in continuation of the project. The effects of parameters on the stability of missile analysed by equations derived in chapter... 

One of the most important issues among defense is the increasing of the defense power using present facilities. Therefore, optimal setting and arrangement of equipment by considering different air-to-earth attack of enemy without knowing of properties and capabilities of available systems may not be possible. So, using defense equipment considering properties of them, and paying attention to existence restrictions and effective elements can have an effective role with the design of suitable algorithm.The main purposes of this thesis are: maximization of the efficiency of a defense system against. aerial invader targets, achieving the best arrangement of defense equipment based on suggested... 

In this research the problem is the development and simulation of Transfer Alignment algorithm for an aerial launch space launch vehicle. In the references there is no complete study on development of this algorithm for the case space launch vehicle. In order to develop the algorithm, the carrying airplane and the space launch navigation systems are considered as the Master INS and Slave INS respectively. First a 6DOF simulation of the airplane is presented. Then the desired inputs for simulation of Master and Slave INS are generated. Also the differences of the inputs of Slave INS caused by the distance between the Master and Slave INS is considered. Master INS performs as an ideal INS and... 

With the advancement of the space industry and the expansion of space missions, the need for satellites and spacecraft with more precise sensors and equipment has increased, which in turn increases the payload mass. In today's world, designing launch vehicles that are merely suitable for the mission is not enough; the launch vehicle must be the best and most appropriate system. The best launch vehicle system is one that not only performs the mission well but is also cost-effective, has higher efficiency, higher reliability, and is easier to maintain. This project aims to develop a multi-disciplinary launch vehicle design software with a graphical interface. In this project, using a... 

The purpose of this thesis is to provide an optimal and online flexible launch vehicle guidance algorithm and method under the occurrence of a random failure in the propulsion system in order to inject the satellite in the nominal orbit/the closest orbit to the nominal orbit. In addition, by recognizing the effects caused by the fault in the propulsion system on the flight dynamics of the launch vehicle, appropriate guidance decisions are applied in analyzes and calculations, and the flexible launch vehicle, according to the amount of error and the time of occurrence of the error and the amount of time left to reach the rated orbit, reaches the nominal orbit or the closest orbit to the... 

Integrated guidance and control (IGC) as a new approach to guidance and control methods has been studied in this thesis. A new approach to nonlinear aerodynamic formulation with backstepping controller has been proposed in order to improve interception. Various curve fitting techniques like Gram-schmidt method has been tested. But finally a planar aerodynamic formulation was used which only varies with angle of attack. Results showed that the proposed method requests smaller control input than the linear IGC formulation and conventional G&C methods, because of more precise knowledge of normal force coefficient. Thus the vehicle experiences smaller angle of attack and normal acceleration.... 

The purpose of this thesis is to design an appropriate controller of a flexible UAV using robust control theory. In the recent decades, researchers have studied the UAVs that were designed for high altitudes and endurances. The applications of these aircrafts can be refer to for missions such as, intelligence surveillances, reconnaissance and aerial surveys. In order to achieve the objectives, the light weight airplane construction and aerodynamic profile is an essential component. That’s why the wings with a high aspect ratio and flexibility are to be used. At first, the robust control, prerequisites, and different methods have been proposed. The next step is the introduction as unmanned... 

Today, a lot of efforts have been done in order to commercialize space travels. Spacecrafts have a lot of components and producing each of them spends high costs. Components such as propellant tanks and boosters are multi segment and are released simultaneously and therefore it is economically feasible to recover them. Due to Parafoil ability in low-cost, soft (no damage to the cargo) and accurate landing, it is gradually replacing parachute. Parafoil can fly long distances after being released, so its landing point could be determined. The aim of the study is to evaluate this scenario in which some segments of launch vehicle (e.g. booster) that are equipped with Parafoil expand their... 

In this project roll channel autopilot of an agile flight vehicle has been studied. In skid-to-turn tactical flight vehicles according to the type of control strategy, for achievment of acceleration commands, the roll angular velocity should be kept near zero. In usual autopilot design, effects of channels on each others is ignored. But three channels of agile flight vehicles have some mutual effects, that consists of kinematic, inertial and aerodynamic couplings. In the case of roll channel dynamics, aerodynamic couplings are dominant and apears because of two factors: roll induced moment and roll cross coupling moment.
After study and aerodynamic modeling of mentioned factors, based... 

In this research, a Reusable Flexible Launch Vehicle (RFLV) design problem is presented by Multi-Disciplinary Design Optimization (MDO) approach in primary design phase. Trajectory, structure, aerodynamic, aeroelasticity and thermal protection system are considered as involved disciplines in design problem. The study purpose will be to obtain an optimal trajectory which meets all the control and structure limitation while the estimating body skin and thermal protection thicknesses base on structural evaluating in re-entry trajectory is in process. The flexible launch vehicle body is considered as a free-free Bernoulli-Euler beam and D’alembert’s principle addresses inertia force in static... 

With the development of fractional order calculus and more accurately modeling of physical phenomena, the problem of controlling these systems, by considering the uncertainties in the system, will become necessary and inevitable. In this thesis, the fractional order transfer function model of a satellite with Coupled rigid-flexible structures is used as the reference work of the research. To control this dynamical system, sliding mode control method, which is one of the robust control methods, has been used. It is clear that it is not possible to directly design a sliding mode controller for a transfer function. For this reason, a fractional order pseudo-state space model is first obtained... 

In this thesis, the multidisciplinary design of liquid propellant satellite launch vehicle has been done by taking into consideration the effects of fuel sloshing. At first, the theory of multidisciplinary design and one-level architecture with the label of multidisciplinary feasibility have been used. In the following, Gravitational Search Algorithm (GSA) and Particle swarm optimization (PSO) have been developed. Then, the multidisciplinary design cycle began with the design of the liquid propellant system. In the propulsion section, the selection of the optimal fuel, the design of the nozzle, motor and the selection of the optimal engine cycle considering the geometric and mass... 

The goal of this thesis is to devise a guidance law that has the required ability and flexibility to construct a variety of return trajectories for a reentry capsule to the atmosphere. One of the commonly used methods for guiding flying vehicles with a fixed initial position and a fixed target is to load the trajectory data into the vehicle's computer memory. But the devised guidance law in this thesis does not require the trajectory data. Based on the relations governing the Bezier curve, it constructs the desired trajectory online. It also has the ability to provide the desired angle of landing and the desired magnitude of final speed. Further studies indicate that this ability is also... 

To make it easier to transition and increase the number of missiles on the launcher, many missiles consider the fins are designed to be foldable. Also, these types of fins can be opened during the flight and therefore reduce the drag force in the initial phase of the flight. One of the disadvantages of this type of design is that the fins may not open during the flight. Moreover, locking the actuator, breaking or destroying some part or all of the control surface of supersonic aircraft due to high speed and temperature and loss of thermal insulation is very probable. This thesis considers the locking, not opening, or even breaking the control surfaces, as well as the destruction of some part... 

The thrust vector control problem is studied for a Satellite with fuel slosh dynamics. The sloshing propellant is modeled as a 3D pendulum. The coupled equations of motion of the satellite and the fuel are expressed in terms of the three dimensional satellite translational velocity vector, the attitude, the angular velocity, and the internal coordinates representing the slosh modes. A nonlinear feedback control law with the idea of backstepping integrator is proposed to control the translational velocity vector and the attitude of the satellite, while attenuating the sloshing modes. A simulation example is included to illustrate the effectiveness of the control law  

Because of advancing fractional calculus and modeling physical phenomena by using fractional calculus more accurately than that by using integer calculus, and also existing uncertainties in models of real world systems, robust stability and performance analysis of fractional order systems are necessary. This thesis deals with the robust -stability analysis of LTI fractional order systems from kind of uncertain typical fractional order systems (UTFOS) and the robust stability analysis of LTI fractional order systems with delays from kind of uncertain retarded type systems (URTS) and uncertain neutral type systems (UNTS) with interval uncertainties. The coefficients of the numerator and the... 

In this writing, Satellite Constellation and Satellite System Design, with a focus on satellite design, for local positioning in Iran, have been considered, in line with the subject of the thesis. The design process have been conducted consistent with the system literature and all the system elements for a satellite Constellation, have been presented as much as possible. In some cases, application of experimental equations in space handbooks do not have significant statistical credit and this fact has been mentioned in those handbooks. For each mission, it is necessary to provide special methods and corresponding requirements. At the end of the satellite design it is found that the design... 

One of the most interesting and at the same time the newest methods to launch a satellite into space is Air Launch or Launch throw the mother aircraft. The placement of the satellite into space by a rocket in specific altitude and speed is separated from the mother aircraft, takes place. The most problems in multi stage rocket launching is trajectory optimization to reaching the maximum height. The survey was conducted using classical optimization methods, which is derived the equations for the gradient based on the calculus of variations. that can be used or modified for emissions control wings and changing the direction of thrust exhaust. It should be noted that in the model of rigid body...